High Mach Number Turbulent Boundary Layer with and without Favorable Pressure Gradient.

reportActive / Technical Report | Accession Number: ADA014730 | Need Help?

Abstract:

Boundary layer profiles of total temperature and total pressure, together with surface pressure and heat transfer rates, in turbulent boundary layers with and without favorable pressure gradients have been measured with a Mach 6 wind tunnel facility. Experimental results were correlated and comparisons between the cases with and without favorable pressure gradient were made. Effects of pressure gradient and upstream history to the boundary layer development were investigated. Numerical results of an existing turbulent boundary layer theory were also compared with present experiments.

Author(s):
No Author(s) Identified
Author Organization(s):
NEW YORK UNIV WESTBURY AEROSPACE AND ENERGETICS LAB
Descriptive Note:
Final rept. 1 Jun 72-1 Mar 75,
Supplementary Note:
See also AD-A014 729, and AD-A014 731.
Pagination:
0133

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
ARL-75-0161
Contract/Grant Number(s):
F33615-72-C-1871
Task Number(s):
706402
Project Number(s):
AF-7064
Monitor Series:
75-0161
 Subject Terms
Modernization Areas:
Hypersonics
Communities of Interest:
No COI(s) Identified
Descriptor(s):
*Turbulent boundary layer, *Hypersonic characteristics, Transport properties, Hypersonic aircraft, Test facilities, Temperature, Pressure gradients, Test methods, Pressure, Measurement, Hypersonic wind tunnels, Numerical methods and procedures, Heat transfer, Enthalpy, Correlation techniques
Field(s)/Group(s):
Fluid Mechanics
Report Date:
1975 Jun 01